Abstract: A method for producing an abradable seal for a turbomachine, such as a turbojet engine low-pressure compressor. The method comprises the following steps performed as follows: (a) preheating of a metal mould in a furnace; (b) filling of the hot mould with a powdery aluminium-based mixture; (c) degassing of the mixture in the mould; (d) compacting of the mixture in the still-hot mould at ambient temperature, so as to solidify the mixture in the mould. The abradable seal is thus produced in angular segments that form tiles. The angular segments are then bonded into a composite casing of the turbomachine.

Abstract: A method for producing an abradable seal for a turbomachine, such as a turbojet engine low-pressure compressor. The method comprises the following steps performed as follows: (a) preheating of a metal mould in a furnace; (b) filling of the hot mould with a powdery aluminium-based mixture; (c) degassing of the mixture in the mould; (d) compacting of the mixture in the still-hot mould at ambient temperature, so as to solidify the mixture in the mould. The abradable seal is thus produced in angular segments that form tiles. The angular segments are then bonded into a composite casing of the turbomachine.